Vilma MAURO, Pedro Antonio De Souza MATOS, Leda Marise VIALTA, Luiz Gilberto BARRETA, Éden Schiavinato DE SOUZA, Matheus Torres Alvarenga SILVA, Marco Antônio Sala MINUCCI, Lucas GALEMBECK, Dermeval CARINHANA JR.
DOI Number: N/A
Conference number: HiSST-2025-155
The minimum total temperature required to sustain a supersonic combustion was investigated in a hydrogen-fueled supersonic combustor directly connected to a shock tunnel facility. The combustor model comprises an isolator (initial constant area section), followed by a single-hole fuel injection point, a flame-holder cavity and an expansion ramp. In order to find the minimum temperature that provides the spontaneous and stable combustion of H2 during the test time, dynamic pressure transducers were installed along the combustor model and a high-speed OH* chemiluminescence emission technique was employed to verify the occurrence of supersonic hydrogen combustion. Total temperatures roughly between 750 and 970 K were reached, a range compatible with the ignition temperature of H2 for hypersonic flows. This configuration led to total pressures of 1.8 to 3.1 MPa. During the experiments, the value of 0.17 ± 0.03 of global equivalence ratio (ϕ) was obtained. The experimental results showed that a stable and spontaneous combustion of H2 occurs with total temperatures greater than 950 K, during the test time.